Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

Detalhes bibliográficos
Autor(a) principal: Mitikov,Yurii
Data de Publicação: 2022
Outros Autores: Shynkarenko,Olexiy
Tipo de documento: Artigo
Idioma: eng
Título da fonte: Journal of Aerospace Technology and Management (Online)
Texto Completo: http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462022000100300
Resumo: ABSTRACT The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of a turbo-pumped liquid propellant rocket engine. This system is the most complex and expensive in a medium-size launch vehicle, after the engine. A new patented methodology of reducing the final mass of a rocket stage is proposed, studied, and validated. The application of the proposed method is efficient at the end of the engine operation sequence during the throttling regime. The calculation method of the helium excess in the high-pressure cylinders uses the model of the real gas. It also involves empirical relations describing nonstationary heat and mass transfer in the system. As an innovative technical solution, the authors propose to estimate excess gas discharge from tanks and cylinders after the engine’s last throttling. The practical application of the research allows saving tenths of kilograms of a payload with the implementation of simple modification in the launcher control program. The research results demonstrated the effectiveness of the methodology on the example of the RD-171 fuel tank pressurization system.
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spelling Reduction of the Pressurization System Final Mass for a Modern Rocket LauncherDry mass reductionPressure reductionLiquid propellant rocket enginesHeliumPressure regulatorsPropellant tanksABSTRACT The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of a turbo-pumped liquid propellant rocket engine. This system is the most complex and expensive in a medium-size launch vehicle, after the engine. A new patented methodology of reducing the final mass of a rocket stage is proposed, studied, and validated. The application of the proposed method is efficient at the end of the engine operation sequence during the throttling regime. The calculation method of the helium excess in the high-pressure cylinders uses the model of the real gas. It also involves empirical relations describing nonstationary heat and mass transfer in the system. As an innovative technical solution, the authors propose to estimate excess gas discharge from tanks and cylinders after the engine’s last throttling. The practical application of the research allows saving tenths of kilograms of a payload with the implementation of simple modification in the launcher control program. The research results demonstrated the effectiveness of the methodology on the example of the RD-171 fuel tank pressurization system.Departamento de Ciência e Tecnologia Aeroespacial2022-01-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462022000100300Journal of Aerospace Technology and Management v.14 2022reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.1590/jatm.v14.1238info:eu-repo/semantics/openAccessMitikov,YuriiShynkarenko,Olexiyeng2022-01-19T00:00:00Zoai:scielo:S2175-91462022000100300Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2022-01-19T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false
dc.title.none.fl_str_mv Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
title Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
spellingShingle Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
Mitikov,Yurii
Dry mass reduction
Pressure reduction
Liquid propellant rocket engines
Helium
Pressure regulators
Propellant tanks
title_short Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
title_full Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
title_fullStr Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
title_full_unstemmed Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
title_sort Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher
author Mitikov,Yurii
author_facet Mitikov,Yurii
Shynkarenko,Olexiy
author_role author
author2 Shynkarenko,Olexiy
author2_role author
dc.contributor.author.fl_str_mv Mitikov,Yurii
Shynkarenko,Olexiy
dc.subject.por.fl_str_mv Dry mass reduction
Pressure reduction
Liquid propellant rocket engines
Helium
Pressure regulators
Propellant tanks
topic Dry mass reduction
Pressure reduction
Liquid propellant rocket engines
Helium
Pressure regulators
Propellant tanks
description ABSTRACT The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of a turbo-pumped liquid propellant rocket engine. This system is the most complex and expensive in a medium-size launch vehicle, after the engine. A new patented methodology of reducing the final mass of a rocket stage is proposed, studied, and validated. The application of the proposed method is efficient at the end of the engine operation sequence during the throttling regime. The calculation method of the helium excess in the high-pressure cylinders uses the model of the real gas. It also involves empirical relations describing nonstationary heat and mass transfer in the system. As an innovative technical solution, the authors propose to estimate excess gas discharge from tanks and cylinders after the engine’s last throttling. The practical application of the research allows saving tenths of kilograms of a payload with the implementation of simple modification in the launcher control program. The research results demonstrated the effectiveness of the methodology on the example of the RD-171 fuel tank pressurization system.
publishDate 2022
dc.date.none.fl_str_mv 2022-01-01
dc.type.driver.fl_str_mv info:eu-repo/semantics/article
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
format article
status_str publishedVersion
dc.identifier.uri.fl_str_mv http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462022000100300
url http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462022000100300
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv 10.1590/jatm.v14.1238
dc.rights.driver.fl_str_mv info:eu-repo/semantics/openAccess
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv text/html
dc.publisher.none.fl_str_mv Departamento de Ciência e Tecnologia Aeroespacial
publisher.none.fl_str_mv Departamento de Ciência e Tecnologia Aeroespacial
dc.source.none.fl_str_mv Journal of Aerospace Technology and Management v.14 2022
reponame:Journal of Aerospace Technology and Management (Online)
instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron:DCTA
instname_str Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
instacron_str DCTA
institution DCTA
reponame_str Journal of Aerospace Technology and Management (Online)
collection Journal of Aerospace Technology and Management (Online)
repository.name.fl_str_mv Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)
repository.mail.fl_str_mv ||secretary@jatm.com.br
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